Blade Forced Response Prediction for Industrial Gas Turbines

Moffatt, Stuart; Weng, Ning; Li, Yansheng; Wells, R. Glenn; He, L.

doi:10.2514/1.6126

Cited by 26 publications

(5 citation statements)

References 8 publications

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“…Figure 14 displays the blade displacement predicted by the 156 aeroelastic ROM at the flutter condition, the third and first modes are the two most dominant ones while the second mode is nearly negligible. The dynamic pressure needed to induce flutter is q ∞ = 1.455x10 6 Pa, nearly 10 times larger than the baseline operating condition at q ∞ = 1.416x10 5 Pa. Hence the rotor made with the material spec- Table 1 is determined to be structurally stable under the chosen operating condition, with a high margin of safety, when only an isolated blade is considered, this finding consistent with that in [5,22].…”

Section: Flutter Analysis For Rotor 67supporting

confidence: 63%

“…The resulting fluid-structure system is a time dependent set of equations describing not only the flow variables in the entire domain, but also the motion of the structure immersed in the fluid. The system can be solved either in the frequency [6] or time domain [5]. The frequency domain approach may be preferred for linear problems for its computational efficiency; however for a nonlinear problem, it is more efficient and accurate to arrive at solution with the time domain approach.…”

Section: Introductionmentioning

confidence: 99%

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Flutter Analysis for Turbomachinery Using Volterra Series

Liou

Yao

2014

Volume 7B: Structures and Dynamics

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The objective of this paper is to describe an accurate and efficient reduced order modeling method for aeroelastic (AE) analysis and for determining the flutter boundary. Without losing accuracy, we develop a reduced order model based on the Volterra series to achieve significant savings in computational cost. The aerodynamic force is provided by a high-fidelity solution from the Reynolds-averaged Navier-Stokes (RANS) equations; the structural mode shapes are determined from the finite element analysis. The fluid-structure coupling is then modeled by the state-space formulation with the structural displacement as input and the aerodynamic force as output, which in turn acts as an external force to the aeroelastic displacement equation for providing the structural deformation. NASA’s rotor 67 blade is used to study its aeroelastic characteristics under the designated operating condition. First, the CFD results are validated against measured data available for the steady state condition. Then, the accuracy of the developed reduced order model is compared with the full-order solutions. Finally the aeroelastic solutions of the blade are computed and a flutter boundary is identified, suggesting that the rotor, with the material property chosen for the study, is structurally stable at the operating condition, free of encountering flutter.

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Section: Flutter Analysis For Rotor 67supporting

confidence: 63%

Section: Introductionmentioning

confidence: 99%

Flutter Analysis for Turbomachinery Using Volterra Series

Liou

Yao

2014

Volume 7B: Structures and Dynamics

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show abstract

“…Described in detail by Moffatt and He (2003), and illustrated in Fig. 1, the decoupled method represents an openloop system, requiring only a single execution of the fluid and structural equations.…”

Section: Overview Of Decoupled Systemmentioning

confidence: 99%

“…The nonlinear harmonic method has been used for decoupled forced response calculations by Moffatt and He (2003) to provide a frequency-domain approach capable of dealing with flow nonlinearities that is typically 30-100 times faster than equivalent multi-passage time-marching calculations (Ning et al, 2003a,b;Chen et al, 2001). Whilst this decoupled method is a linearized approach, it is not restricted to linear flow conditions.…”

Section: Introductionmentioning

confidence: 99%

On decoupled and fully-coupled methods for blade forced response prediction

Moffatt¹,

He²

2005

Journal of Fluids and Structures

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“…At the same time, the blades are subjected to periodic aerodynamic excitation in resonant conditions. The approach proposed in this Note is to design how to avoid dangerous resonances in the operating range [1]. This is a qualitative standard design practice to avoid resonance using the Campbell diagram.…”

Section: Introductionmentioning

confidence: 99%